CN117073966A - Temporary flushing type three-sound-velocity wind tunnel layout structure - Google Patents
Temporary flushing type three-sound-velocity wind tunnel layout structure Download PDFInfo
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- CN117073966A CN117073966A CN202311345056.6A CN202311345056A CN117073966A CN 117073966 A CN117073966 A CN 117073966A CN 202311345056 A CN202311345056 A CN 202311345056A CN 117073966 A CN117073966 A CN 117073966A
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- 238000011010 flushing procedure Methods 0.000 title claims abstract description 19
- 238000012360 testing method Methods 0.000 claims abstract description 48
- 230000007246 mechanism Effects 0.000 claims abstract description 35
- 241001640558 Cotoneaster horizontalis Species 0.000 claims abstract description 32
- 230000001105 regulatory effect Effects 0.000 claims description 18
- 239000007787 solid Substances 0.000 claims description 11
- 230000009467 reduction Effects 0.000 claims description 2
- 238000004080 punching Methods 0.000 claims 1
- 230000030279 gene silencing Effects 0.000 abstract description 6
- 230000008602 contraction Effects 0.000 abstract description 5
- 238000010276 construction Methods 0.000 abstract description 3
- 230000007547 defect Effects 0.000 abstract 1
- 239000007921 spray Substances 0.000 description 12
- 238000000034 method Methods 0.000 description 8
- 230000008569 process Effects 0.000 description 4
- 238000012797 qualification Methods 0.000 description 4
- 230000000087 stabilizing effect Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000001276 controlling effect Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention relates to the field of wind tunnels and discloses a temporary flushing type three-sonic wind tunnel layout structure which comprises a gas storage tank, a stable section, a flexible wall spray pipe, a test section and a super-expansion section, wherein the gas storage tank is connected with the stable section through a pipeline, the stable section is connected with a contraction section, the contraction section is connected with the flexible wall spray pipe, the flexible wall spray pipe is connected with the test section, the test section is connected with the super-expansion section, an ejector is arranged between the super-expansion section and a sub-expansion section, and the sub-expansion section is connected with a silencing tower. According to the invention, up to seven working modes are realized by replacing the test section, enabling or not enabling the gate finger mechanism and enabling or not enabling the ejector, and the working modes meet different test requirements of wind tunnel users to the greatest extent, so that the comprehensive construction cost of the wind tunnel is reduced to the lowest, the utilization rate of the wind tunnel is maximized, and the defects that one wind tunnel is constructed in one requirement and the utilization rate of the wind tunnel with a single requirement for construction is low in a long air window period are overcome.
Description
Technical Field
The invention relates to the field of wind tunnels, in particular to a temporary flushing type trisonic wind tunnel layout structure.
Background
The temporary flushing type wind tunnel is characterized in that the upstream of the wind tunnel is a gas storage tank, the downstream of the wind tunnel is air, the wind tunnel operation pressure is provided by the gas storage tank pressure, and the gas storage tank pressure continuously drops along with the increase of the wind tunnel operation time due to the limited gas storage tank volume until the gas storage tank pressure does not meet the wind tunnel operation pressure requirement, and the wind tunnel stops operating at the moment. Trisonic wind tunnels refer to the operational Mach range of the wind tunnel covering subsonic, transonic and supersonic speeds. The existing temporary flushing type trisonic wind tunnel layout generally has the following problems: the Mach number upper limit is usually 2.0 or 3.0, and can rarely reach more than 4.0 or 4.0, so that the wind tunnel test requirements of modern aircrafts, particularly critical space aircrafts, are not met; secondly, a plurality of solid block spray pipes are generally adopted, one solid block spray pipe corresponds to one wind tunnel Mach number to realize different Mach numbers of the wind tunnel, so that the layout problem is that after the processing of the solid block spray pipes is finished, the molded surface is fixed, the flow field quality of the solid block spray pipes is generally in the national army standard qualified level, in addition, the time required for changing the spray pipes is long, and the wind tunnel operation efficiency is low; thirdly, in the case of sub-transonic speed, the accuracy of the traditional control mode for controlling the Mach number of the wind tunnel through the pressure regulating valve is not high, and the Mach number control accuracy of the qualification index delta M is not more than 0.005; fourthly, the wind tunnel loss is usually larger, so that the operation pressure is higher, that is, the load born by the wind tunnel test model is larger, and a certain safety risk exists. Fifthly, a wind tunnel is usually built aiming at one to two requirements, the wind tunnel operation mode is single, for example, subsonic high-precision operation is pursued, the precision requirement is usually ignored, but the scene with high efficiency requirement is usually omitted, for example, supersonic high-precision operation is pursued, a plurality of special models or large-size models are ignored, the test can be safely carried out only with the aid of a model clamping mechanism, and the wind tunnel utilization rate is usually low, and the empty window period is long.
Disclosure of Invention
In order to solve the technical problems in the prior art, the invention provides a temporary flushing type three-sound-velocity wind tunnel layout structure.
The invention adopts the following specific scheme: the utility model provides a three sound velocity wind tunnel layout structure of dashing temporarily, wind tunnel layout structure includes gas holder, stable section, gentle wall spray tube, test section, super section of expanding, the gas holder passes through pipe connection with stable section, stable section is connected with the shrink section, the shrink section is connected with gentle wall spray tube, gentle wall spray tube is connected with test section, test section is connected with super section of expanding, super section of expanding sets up the ejector with inferior section of expanding, inferior section of expanding is connected with the amortization tower.
The gas storage tank is a medium-pressure gas storage tank, and the pressure born by the gas storage tank is less than 2.0MPa.
The flexible wall spray pipe is a rectangular section flexible wall spray pipe, and the upper wall surface and the lower wall surface of the flexible wall spray pipe are molded surfaces.
The pipeline is provided with a valve system, the valve system comprises a butterfly valve and a pressure regulating valve, the butterfly valve comprises a main path butterfly valve and a bypass butterfly valve, the main path butterfly valve and the bypass butterfly valve are arranged in parallel, and the pressure regulating valve adopts an annular gap pressure regulating valve.
The super-expansion section is a super-expansion section with an adjustable section.
The experimental section comprises a sub-transonic speed section in a residence chamber, wherein the sub-transonic speed section is a straight hole wall section, an upper straight hole wall and a lower straight hole wall of the straight hole wall section are both straight hole walls, and a left side wall and a right side wall of the straight hole wall section are both solid walls.
The residence chamber of the test section comprises a second supersonic speed section, and model clamping mechanisms are respectively arranged on the upper wall and the lower wall in the second supersonic speed section.
The first diamond-shaped area in the flexible wall spray pipe is a first supersonic section.
The super-expansion section inlet is internally provided with a model type attitude angle changing mechanism, and the middle part of the super-expansion section is provided with a grid finger mechanism.
The ejector is a slit supersonic ejector with a rectangular section. Compared with the prior art, the invention has the following beneficial effects:
the invention discloses a temporary flushing type three-sound-velocity wind tunnel layout structure, which realizes up to seven working modes through the layout planning of wind tunnel sections, each mode has unique advantages, can meet different test requirements of wind tunnel users, furthest utilizes one wind tunnel layout to meet as many test requirements as possible, maximizes the wind tunnel utilization rate and greatly reduces the cost of comprehensively constructing a plurality of wind tunnels. In addition, the wide speed range of Mach numbers 0.3-4.2 is realized, the Mach number upper limit of the trisonic wind tunnel is expanded, and the wind tunnel test capability is improved.
On the other hand, the invention adopts the medium-pressure air storage tank as a common air source of the wind tunnel main pipeline and the ejector pipeline, thereby avoiding the increased cost for constructing a separate air source for the ejector. The invention adopts the flexible wall spray pipe to replace a plurality of fixed block spray pipes, effectively utilizes the flexible wall spray pipe, and greatly improves the quality of the wind tunnel flow field by fine adjustment of the spray pipe molded surface.
Drawings
FIG. 1 is a schematic diagram of a layout structure of a temporary flushing type trisonic wind tunnel according to the present invention;
FIG. 2 is a schematic illustration of a test section of the present invention with a sub-transonic section disposed therein;
FIG. 3 is a schematic diagram of a test section with a second supersonic section disposed therein;
FIG. 4 is a schematic illustration of a super-expansion segment according to the present invention;
fig. 5 is a top view of fig. 4.
Symbol description:
1. a gas storage tank; 2. butterfly valve; 3. a pressure regulating valve; 4. a stabilizing section; 5. a constriction section; 6. a flexible wall nozzle; 7. a test section; 8. super-expanding section; 9. an ejector; 10. sub-expanding; 11. a silencing tower; 12. a gate finger mechanism; 13. a residence chamber; 14. an upper wall; 15. a lower wall; 16. a mold clamping mechanism; 17. a sub-transonic section; 18. a model attitude angle changing mechanism; 19. a first supersonic segment; 20. a second supersonic segment; 21. a first plate segment; 22. a second plate segment; 23. a third plate segment; 24. and a fourth plate section.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention is described below by means of specific embodiments shown in the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the invention. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present invention.
The utility model discloses a three sound velocity wind tunnel layout structure of dashing temporarily, this embodiment discloses a three sound velocity wind tunnel layout structure of dashing temporarily, wind tunnel layout structure includes gas holder 1, stable section 4, gentle wall spray tube 6, test section 7, super section 8 that expands, gas holder 1 passes through the pipe connection with stable section 4, stable section 4 is connected with shrink section 5, shrink section 5 is connected with gentle wall spray tube 6, gentle wall spray tube 6 is connected with test section 7, test section 7 is connected with super section 8 that expands, super section 8 and inferior section 10 that expands set up ejector 9 between, inferior section 10 that expands is connected with the silencing tower 11.
The gas storage tank 1 is a medium-pressure gas storage tank, and the bearing pressure of the gas storage tank 1 is less than 2.0MPa. The air storage tank 1 is used as a common air source of a wind tunnel main path and an ejector 9 pipeline.
The flexible wall spray pipe 6 is a rectangular section flexible wall spray pipe, and the upper wall surface and the lower wall surface of the flexible wall spray pipe 6 are molded surfaces. The pipeline is provided with a valve system, the valve system comprises a butterfly valve 2 and a pressure regulating valve 3, the butterfly valve 2 comprises a main path butterfly valve and a bypass butterfly valve, the main path butterfly valve and the bypass butterfly valve are arranged in parallel, and the pressure regulating valve 3 adopts an annular gap pressure regulating valve.
The super-expansion section 8 is a super-expansion section with an adjustable section. The model attitude angle changing mechanism 18 is arranged in the inlet of the super-expansion section 8, and the grid finger mechanism 12 is arranged in the middle of the super-expansion section 8. The ejector 9 is a slit supersonic ejector with a rectangular section.
In one embodiment, the residence chamber 13 of the test section 7 includes a sub-transonic section 17, the sub-transonic section 17 is a straight hole wall section, the upper straight hole wall and the lower straight hole wall of the straight hole wall section are both straight hole walls, and the left side wall and the right side wall of the straight hole wall section are both solid walls.
In one embodiment, the residence chamber 13 of the test section 7 includes a second supersonic section 20, and the upper wall 14 and the lower wall 15 in the second supersonic section 20 are both provided with a model clamping mechanism 16. The first diamond-shaped region in the flexible-wall nozzle 6 is a first supersonic section 19.
The operation Mach number range of the temporary flushing type three-sound-velocity wind tunnel layout structure in the embodiment is 0.3-4.2, and the advanced level is achieved. The test section 7 is a replaceable section, the super-expansion section 8 is a section capable of moving back and forth along the axis of the wind tunnel, and the rest sections are fixed sections. Seven working modes can be realized by means of replacing the test section 7, enabling or not enabling the grid finger mechanism 12 in the super-expansion section 8, enabling or not enabling the ejector 9 and the like, and the seven working modes are respectively mode one: the subtransonic normal operation (corresponding to the subtransonic section 17, the gate finger mechanism 12 is not started, and the ejector 9 is not started) is characterized in that the wind tunnel is simple to control and high in efficiency, but the Mach number control precision only reaches the national army standard qualification level; mode two: the accurate operation of the sub-transonic speed (corresponding to the sub-transonic speed section 17, the gate finger mechanism 12 is started, the ejector 9 is not started), and the method is characterized in that Mach number control precision can reach the advanced level of national army standards, a wind tunnel can be operated at normal pressure or can be pressurized, the Reynolds number of a wind tunnel test can be improved under the condition of pressurized operation, the method is closer to the real environment, but the safety of a test model is a problem which needs to be solved under the condition of pressurized operation, and meanwhile, the mode control is relatively complex; mode three: the sub-transonic speed accurate low-pressure operation (corresponding to the sub-transonic speed section 17, the gate finger mechanism 12 is started and the ejector 9 is started) is characterized in that Mach number control accuracy can reach the advanced national standard level, wind tunnel low pressure is lower than one atmosphere pressure operation, high-altitude low-pressure environment can be effectively simulated, but the control is most complex, the air consumption is large, and the efficiency is low; mode four: the supersonic speed is precisely operated without injection (corresponding to the first supersonic speed section 19, the grid finger mechanism 12 is not started, and the injector 9 is not started), and the method is characterized in that the supersonic speed flow field has high quality, but the total pressure of a wind tunnel is high, which is unfavorable to a large-size model and easy to bring about safety problems; mode five: the supersonic special type non-injection operation (corresponding to the second supersonic section 20, the gate finger mechanism 12 is not started, and the injector 9 is not started) is characterized in that the test section 7 is internally provided with a model clamping mechanism 16, the safety is higher than that of the first supersonic section 19, and the supersonic special type non-injection operation is very beneficial to some special-shape or large-size test models, and because the injector 9 is not started, the wind tunnel total pressure is high, the model usually operates below Mach number 2.5, and the quality of a flow field only can reach the national standard qualification level; mode six: the supersonic speed precise belt is guided to run (corresponding to the first supersonic speed section 19, the grid finger mechanism 12 is not started, and the ejector 9 is started), and is characterized by high supersonic speed flow field quality, low wind tunnel total pressure, high wind tunnel air consumption and high cost; mode seven: the supersonic special belt is guided to run (corresponding to the second supersonic section 20, the grid finger mechanism 12 is not started, and the ejector 9 is started), and is characterized in that the model clamping mechanism 16 is arranged in the test section 7, the total wind tunnel is low, the safety of the test model is highest, the supersonic special belt is very beneficial to some models with large size or special shape, but the wind tunnel has the maximum air consumption, and the flow field quality only can reach the national standard qualification level.
Examples
The temporary flushing type three-sound-velocity wind tunnel layout structure is formed by sequentially connecting a gas storage tank 1, a valve system, a stabilizing section 4, a contraction section 5, a flexible wall spray pipe 6, a test section 7, a super-expansion section 8, an ejector 9, a sub-expansion section 10 and a silencing tower 11 from upstream to downstream of the wind tunnel, and air flows out of the gas storage tank 1 and finally is discharged through the silencing tower 11.
The flexible wall spray pipe 6 is a binary rectangular section full flexible wall spray pipe, the upper wall surface and the lower wall surface of the flexible wall spray pipe 6 are molded surface walls, mach numbers can be 0.3-4.2, and the left side wall and the right side wall of the flexible wall spray pipe 6 are parallel solid walls.
The pipeline is provided with a valve system, the valve system comprises a butterfly valve 2 and a pressure regulating valve 3, the butterfly valve 2 comprises a main path butterfly valve and a bypass butterfly valve, the main path butterfly valve and the bypass butterfly valve are arranged in parallel, and the pressure regulating valve 3 adopts an annular gap pressure regulating valve. The butterfly valve plays roles of cutting off and switching on an air source, and before the main path butterfly valve is opened, the bypass butterfly valve must be opened first, so that the pressure on two sides of the bypass butterfly valve is balanced. The pressure regulating valve 3 adopts an annular slit valve, and has the function of regulating and controlling the opening of the pressure regulating valve 3 through a control system along with the reduction of the air source pressure in the wind tunnel operation process, ensuring that the air flow pressure in the stabilizing section 4 is stabilized at a certain operation pressure value and maintaining the normal operation of the wind tunnel.
The air flow from the air storage tank 1 enters the flexible-wall spray pipe 6 after being rectified and reduced by the stabilizing section 4 and the contracting section 5, and the flexible-wall spray pipe 6 is an important component for ensuring that the test section 7 obtains uniform air flow with designed Mach number in a wind tunnel. The invention adopts the binary full flexible wall spray pipe to achieve the purpose of realizing high precision of wide speed range M=0.3-4.2, the wall surface of the flexible wall spray pipe 6 is a surface wall, different Mach number surface is formed by driving the surface driving device, the left side wall and the right side wall are smooth solid walls, and pressure measuring holes are arranged, so that whether the Mach number of the spray pipe is reached can be checked. The first diamond-shaped area inside the flexible-wall spray pipe 6 is used as a first supersonic speed section, and in the test section, the flow field is high in quality, so that the flexible-wall spray pipe is suitable for a high-precision supersonic speed test working mode four and a high-precision supersonic speed test working mode six.
The downstream of the flexible wall spray pipe 6 is a sub-transonic speed section and can be replaced by a second supersonic speed section, wherein the sub-transonic speed section is a test section 7 of a straight hole wall, the upper straight hole wall and the lower straight hole wall are straight hole walls, the aperture ratio is 22.5%, the interference of the wind tunnel hole wall to a test model is minimum under the aperture ratio through test comparison, and the left side wall and the right side wall are solid walls. The four walls of the second supersonic section are smooth solid walls, and unlike the first supersonic section, the upper wall 14 and the lower wall 15 of the second supersonic section are provided with a model clamping mechanism 16, the model can bear impact load in the wind tunnel starting process, the impact load is larger for the model with particularly long or large span, and damage risks exist in the wind tunnel starting process, so that the model clamping mechanism 16 is required to clamp the model in the wind tunnel starting process, the protection effect is achieved, and after the wind tunnel is started, the model clamping mechanism 16 is retracted into the upper wall 14 and the lower wall 15. The sub-transonic section 17 and the second supersonic section 20 are not arranged in series, but are interchangeable, and the lengths thereof can be the same or different, and the lack of length can be compensated by connecting a moving sleeve section below the super-expansion section 8.
The super-expansion section 8 is arranged at the downstream of the test section 7, in order to shorten the whole length of the wind tunnel as much as possible, the super-expansion section 8, the support section and the grid finger section are integrated, the model attitude-changing angle mechanism 18 is arranged in the first plate section 21 of the inlet part of the super-expansion section 8, the grid finger mechanism 12 is arranged in the third plate section 23 in the middle part of the super-expansion section 8, and the non-conventional grid finger mechanism 12 is arranged in front of the super-expansion section 8. The side wall of the super-expansion section 8 adopts a four-plate-section adjustable wall type, a first plate section 21 and a second plate section 22 form a contraction part of the profile of the super-expansion section 8, a third plate section 23 is an equal straight part of the profile of the super-expansion section 8, and a fourth plate section 24 is an expansion part of the profile of the super-expansion section 8. The width between the side walls of the super-expansion section 8 can be adjusted through the driving of the side wall plate driving mechanism, so that different super-expansion section 8 profiles are formed, and different wind tunnel Mach numbers are corresponding to the different profiles. As the model attitude-changing angle mechanism 18 is added to the inlet of the super-expansion section 8, the width and the height of the inlet of the super-expansion section 8 can be adjusted. The grid finger mechanism 12 in the middle of the super-expansion section 8 is fully retracted during the supersonic speed test, and the air flow sectional area is regulated by controlling the expansion and contraction amount of the grid finger mechanism 12 in real time during the sub-transonic speed test to form a blocking throttle, so that the Mach number of the air flow of the test section 7 is accurately controlled in real time. The Mach number control precision can be improved from the conventional delta M less than or equal to 0.005 to delta M less than or equal to 0.001 by utilizing the grid finger mechanism 12.
The ejector 9 is arranged at the downstream of the super-expansion section 8, the ejector 9 is used as a device for conveying fluid, the other low-pressure fluid is ejected by means of high-speed flow formed after the high-pressure fluid flows through the nozzle, and energy exchange and material mixing are carried out in a mixing chamber of the ejector 9, so that the conveying purpose is finally achieved. When the ejector 9 acts on the wind tunnel, the ejector is mainly used as a driving device of the wind tunnel, and the low-pressure low-speed airflow from the upstream is driven and then discharged through the silencing tower 11. Considering that the interference to the wind tunnel flow field is reduced as much as possible and no extra resistance loss is brought, the ejector 9 adopts a four-wall slit supersonic ejector, the ejected air flow comes from the super-expansion section 8, the section of the ejector 9 is a rectangular section instead of a common circular section and is mainly matched with the rectangular section of the super-expansion section, and if the circular section is adopted, a rectangular-to-round section is also required to be arranged after the super-expansion section, so that the wind tunnel length is lengthened, and the cost is increased.
The invention effectively improves the wind tunnel sub-transonic Mach number adjusting precision, reduces the overall length of the wind tunnel and reduces the wind tunnel construction cost; the super-expansion section 8 and the ejector 9 are combined for use, so that the wind tunnel operating pressure is reduced by more than half under the same Mach number, and the use safety of the wind tunnel is improved.
The foregoing drawings and description are only one embodiment of the present invention, but the specific scope of the present invention is not limited to the above description, and any simple replacement or modification within the scope of the technical idea disclosed in the present invention and according to the technical scheme of the present invention should be within the scope of the present invention.
Claims (10)
1. The utility model provides a three sound velocity wind tunnel layout structure of dashing temporarily, its characterized in that, wind tunnel layout structure includes gas holder (1), stable section (4), gentle wall spray tube (6), test section (7), super section of expanding (8), gas holder (1) and stable section (4) pass through the pipe connection, stable section (4) are connected with shrink section (5), shrink section (5) are connected with gentle wall spray tube (6), gentle wall spray tube (6) are connected with test section (7), test section (7) are connected with super section of expanding (8), set up ejector (9) between super section of expanding (8) and sub-section of expanding (10), sub-section of expanding (10) are connected with noise reduction tower (11).
2. The temporary flushing type three-sonic wind tunnel layout structure according to claim 1, wherein the flexible wall spray pipe (6) is a rectangular section flexible wall spray pipe, and both the upper wall surface and the lower wall surface of the flexible wall spray pipe (6) are profile walls.
3. The temporary flushing type three-sonic wind tunnel layout structure according to claim 2, wherein a valve system is arranged on the pipeline and comprises a butterfly valve (2) and a pressure regulating valve (3), the butterfly valve (2) comprises a main path butterfly valve and a bypass butterfly valve, the main path butterfly valve and the bypass butterfly valve are arranged in parallel, and the pressure regulating valve (3) adopts an annular gap pressure regulating valve.
4. A temporary flushing type trisonic wind tunnel layout structure as claimed in claim 3, characterized in that the super-expansion section (8) is a super-expansion section with an adjustable cross section.
5. The temporary flushing type three-sonic wind tunnel layout structure according to claim 4, wherein the first diamond-shaped area in the flexible wall jet pipe (6) is a first supersonic section (19).
6. The temporary flushing type three-sound-velocity wind tunnel layout structure according to claim 5, wherein a model attitude-changing angle mechanism (18) is arranged inside an inlet of the super-expansion section (8), and a grid finger mechanism (12) is arranged in the middle of the super-expansion section (8).
7. The temporary punching type trisonic wind tunnel layout structure according to any one of claims 1-6, characterized in that a sub-transonic section (17) is included in a residence chamber (13) of the test section (7), the sub-transonic section (17) is a straight hole wall section, an upper straight hole wall and a lower straight hole wall of the straight hole wall section are both straight hole walls, and a left side wall and a right side wall of the straight hole wall section are both solid walls.
8. The temporary flushing type trisonic wind tunnel layout structure according to any one of claims 1-6, characterized in that a second supersonic section (20) is included in a resident chamber (13) of the test section (7), and a model clamping mechanism (16) is arranged on an upper wall (14) and a lower wall (15) in the second supersonic section (20).
9. The temporary flushing type three-sound-velocity wind tunnel layout structure according to claim 1, wherein the air storage tank (1) is a medium-pressure air storage tank, and the pressure born by the air storage tank (1) is less than 2.0MPa.
10. The temporary flushing type three-sound-velocity wind tunnel layout structure according to claim 1, wherein the ejector (9) is a slit supersonic ejector with a rectangular cross section.
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| CN202311345056.6A CN117073966B (en) | 2023-10-18 | 2023-10-18 | Temporary flushing type three-sound-velocity wind tunnel layout structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117494322A (en) * | 2024-01-02 | 2024-02-02 | 中国人民解放军国防科技大学 | Design method, device, equipment and medium of sub-span supersonic flow field controllable spray pipe |
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